Front: Text describes action on various war fronts: Tunisia, Russia, Southwest Pacific, Air offensive, Aleutians. Large world map is keyed to text and illustrates time zones around the world. Inset map shows Tunisia. Includes photographs: troops receiving daily news summaries, bombers in flight, M-10 tank destroyers, and a German Mark VI. Back: British Aircraft. 19 aircraft are identified by sketch or photograph. Text provides description of each.

Front: Text describes action on various war fronts: Russia, Solomons, New Guinea, Aleutians, Bolivia, Tunisia, Air offensive. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Sicily and Tunis. Includes photographs: Malaria control, Super block-buster [8,000 lb. aerial bomb], Change of ownership [captured Mercedes Benz troop-carrier], Bren-gun carriers support British Grenadiers in Kasserine Pass, Italian troops in the African war zone. Back: The Marine Corps. A unified fighting force. Graphic image shows helmeted Marine soldiers with rifles attacking a tropical island with ships and transport boats in background, as well as various photos of parachutes, bombardments, etc.

Front: Text describes action on various war fronts: Tunisia -- Southwest Pacific -- Russia -- Mediterranean. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Allied drive in Tunisia -- Japanese controlled areas throughout the Southwest Pacific. Includes photographs: Helping Rommel's run [puppy stationed atop a Vickers machine gun] -- So he can fight (Staff Sergt. Hollers clerks at the San Angelo AAF Bombardier School in Texas) -- Blimp training. Back: Tunisia, map with inset showing location of Tunisia in the Mediterranean area.

Text describes action on various war fronts: Tunisia, Raid on Japan, Southwest Pacific, Italy, Air offensive, Russia, Aleutians. Large world map is keyed to text. Shows United Nations countries, Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Inset maps show Italy, Sardinia, and northern Tunisia; Axis held areas in Tunisia; Nazi held areas around the Sea of Azov. Back: Fox Holes: Dig!..Or Die! Photographs and illustrations describing proper fox hole preparation and use.

Map displays soil types along with creeks, lakes, rivers, tanks, ranches, roads, railroads, power transmission lines, Texas Agricultural Experiment Stations, towns, and Texas Land Office blocks and surveys. Includes legend and symbols. A polyconic projection, 1927 North American Datum. "Horizontal control by U.S.G.S. and U.S. C. and G. S. 10000 foot grid based upon Texas (South-central) system of plane coordinates."

Text describes climate, agriculture, soils, and crops of Dimmit County, Texas.

Describes the organization and functions of the U.S. Army Quartermaster Corps.

Discusses the purpose and usage of the pneumatic pontoon bridge M3 by infantry in the field. Covers construction, deployment, and maintenance.

"The following surveys on the vibration response of the P-40 rudder and fin-rudder assembly were conducted during the fall of 1942 for the purpose of obtaining information on the flutter characteristics of high-speed airplanes of known performance. The tests on the rudder alone were made with the rudder suspended in a floating condition; the tests on the fin-rudder unit were made with the fin rigidly fastened to a concrete base" (p. 1). A variety of figures and diagrams for the assembly are provided.

Report presenting a study of the flutter characteristics of the P-47 tail assembly, which included replacing the original fabric-covered rudder with a metal-covered rudder and reinforcing the fin. Figures are provided for different configurations and the cycles per second under the same conditions are provided.

"The variation in the necessary aileron control and in the time required to bank to 45 degrees and 90 degrees with altitude and radii of gyration for a typical fighter or a pursuit airplane have been computed and are presented herein." The lateral motions and impact pressure for several conditions of flight are provided. The report concludes that "the aileron system...should be designed for rolling-moment requirements at high altitude and the hinge-moment limitations at low altitude".

Report presenting the thermal and pressure drop performance data of a slotted-fin Stewart-Warner exhaust gas and ventilating air heat exchanger. Three different crossflow air shrouds were used in testing. The rate of heat transfer was about the same for each shroud, but the static pressure drops varied greatly.

Report presenting observations made of the air flow around a Martin PBM-3 flying boat. The observations are part of an analysis to aid in the determination of possible methods of reducing the air drag of the airplane. The behavior of the tufts on the hull and tip floats at various airplane speeds by still and moving pictures taken from an accompanying airplane.

Report presenting testing to study the effects of a typical nacelle on the characteristics of a thick low-drag airfoil that was shown to be subject to separation difficulties due to leading edge roughness. This testing confirmed the results of previous tests which indicated that the airfoil was unconservative with respect to separation difficulties. Results regarding the internal-flow measurements and corresponding drag increments, external drag, leading-edge roughness and nacelle combination, and section lift comparisons are provided.

This is an account of an investigation in which oscillations were discovered in the laminar boundary layer along a flat plate. These oscillations were found during the course of an experiment in which transition from laminar to turbulent flow was being studied on the plate as the turbulence in the wind stream was being reduced to unusually low values by means of damping screens. The first part of the paper deals with experimental methods and apparatus, measurements of turbulence and sound, and studies of transition. A description is then given of the manner in which oscillations were discovered and how they were found to be related to transition, and then how controlled oscillations were produced and studied in detail.

A detailed method for determining the jet-boundary corrections for reflection-plane models in rectangular wind tunnels is presented. The method includes the determination of the tunnel span local distribution and the derivation of equations for the corrections to the angle of attack, the lift and drag coefficients, and the pitching-, rolling-, yawing-, and hinge-moment coefficients. The principle effects of aerodynamic induction and of the boundary-induced curvature of the streamlines have been considered. An example is included to illustrate the method. Numerical values of the more important corrections for reflection-plane models in 7 by 10-foot closed wind tunnels are presented.

"Results of flight tests of the performance and cooling characteristics of three NACA D cowlings and of a conventional NACA D cowling on the XP-42 airplane are summarized and compared. The D cowling is, in general, characterized by the use of an annular inlet and diffuser section for the engine-cooling air. The D cowlings tested were a long-nose high-inlet-velocity cowling, a short-nose high-inlet-velocity cowling, and a short-nose low inlet-velocity cowling" (p. 371).

From Summary: "An analysis has been made of a considerable amount of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. It was found that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter. This parameter was chosen as the ratio of the displacement thickness to the momentum thickness of the boundary layer. The variables that control the development of the turbulent boundary layer apparently are: (1) the ratio of the nondimensional pressure gradient, expressed in terms of the local dynamic pressure outside the boundary layer and boundary-layer thickness, to the local skin-friction coefficient and (2) the shape of the boundary layer. An empirical equation has been developed in terms of these variables that, when used with the momentum equation and the skin-friction relation, makes it possible to trace the development of the turbulent boundary layer to the separation point."

General formulas are given for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of the side-force derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angle ranges from 15 degrees or 20 degrees to 60 degrees.

From Introduction: "The purpose of this paper is to outline a suggested form of presentation of the results of a stability and control investigation in terms of flying qualities as defined in reference 1 and to systematize and review briefly the analytical work required for this type of presentation. No effort is made to specify definite test procedures."

Report presenting compressibility phenomena under flight conditions on the XF2A-2 airplane, which was subjected to a series of dives and pull-outs at speeds up to 550 miles per hour corresponding to Mach numbers of 0.74. Results regarding time histories, pressure data, drag coefficient, and elevator control force are provided.

Report presenting tests in the free-flight tunnel to determine the effect of the fuselage length and the aspect ratio and size of the vertical tail on lateral stability and control. Fuselages of two different lengths and various vertical tail surfaces were used on a powered model in the investigation. Results regarding the test conditions, flight tests, and force tests are provided.

Report presenting a flight investigation of the flying qualities and stalling characteristics of a North American XP-51 airplane. The short-period longitudinal oscillation disappeared within one cycle in all conditions tested. Requirements for satisfactory stalling characteristics were met in all respects except for stall warning.

Report presenting an investigation in the NACA 15-foot free-spinning tunnel to determine the effect of wing leading-edge slots on spin and recovery characteristics. The results indicate that recovery will generally be slower with the slots open than with them closed and the spin will be flatter and at a lower rate of descent.